Long-range guided athodyd



p 38, 1954 H. H. PORTER ET AL ,690,314

LONG-RANGE GUIDED ATHODYD Filed Dec. 15, 1949 2 Sheets-Sheet l FIG! INVENTOR. HENRY H. PORTER ROBERT J. VICARS I i ATTORNEY Sept 23, 1954 H. H. PORTER ET AL LONG-RANGE GUIDED ATHODYD 2 Sheets-Sheet 2 Filed Dec. 15, 1949 INVENTOR. HENRY H. PORTER ROBERT J. VICARS Y a XZMW ATTORNEY llllllllllllllllllllllm=l\l\l\llll llllllllllll mm mm 2 mm 2 Patented Sept. 28, 1954 i1 H'E'ED STATES PATENT @FFKQE LONG-RANGE GUIDED ATHODYD Application December 15, 1949, Serial No. 133,088

6 Claims. (Cl. 24414) This invention relates generally to guided missiles. More particularly it relates to a guided missile designed to be effective over extremely long ranges.

Guided missiles operating at speeds in excess of that of sound are becoming increasingly im portant for long-range warfare. Prominent among such missiles are the ram-jets, which are self-propelling, use readily available liquid fuel and are capable of being guided while in aerial travel. Ram-jet missiles as developed up to the present time, however, have made no provision for the uniformly satisfactory packaging of components, such as guidance and control mechanisms, fuel storage and fuel injectors, burners, and the warhead.

One of the principal objects of the present invention, therefore, is to provide a long range guided missile having a compartmented inner body, the compartments of which are designed to carry, in their proper operative positions, the warhead, and the guidance and other operating components of the missile.

Another object of the invention is to provide a missile which is simple in arrangement and which can, therefore, be manufactured in quantity with a minimum number of engineering difficulties.

Other objects and many of the attendant advantages of this invention will be appreciated readily as the same becomes understood by reference to the following detailed description, when considered in connection with the accompanying drawings, wherein:

Fig. 1 is a longitudinal section of a missile according to the present invention, some of the parts being shown in elevation;

Fig. 2 is an enlarged detail axial section of the forward end portion of the missile;

Fig. 3 is an axial section of the missile, partly in side elevation;

Fig. 4 is a detail on an enlarged scale, showing the fuel pressurizing arrangement, and

Fig. 5 is a front view of the missile.

Referring now more particularly to the drawings, wherein like parts are designated by like reference numerals throughout the views, the numeral l indicates generally the missile of the present invention, said missile including a tubular body constituting an outer shell 2 which carries main Wings 3, 3 and guiding vanes l, 4 and 5, 5. An inner body 6 is mounted concentrically within the outer shell 2, by means to be described hereinafter, and extends throughout the major portion of its length.

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The wings 3, 3 are preferably of relatively great area. In normal flight, these wings have sufficient angle of attack to provide adequate support for the missile. Inasmuch as the density of the atmosphere is very low at the extreme altitudes at which supersonic missiles can travel efficiently, such large wing areas are requisite, to provide sufiicient lift.

The guiding or steering vanes A, 4 may operate in the same general axial plane as the wings 3, 3 but may be turned about a horizontal axis, as may be necessary to maintain the desired angle of attack of the supporting wings.

The guiding or steering vanes 5, 5 are normally in the vertical axial plane of the missile, but may be turned about a vertical axis, to steer the missile to the right or left, as required. Movement of the vanes 4, 4 and 5, 5 is controlled by guidance and control apparatus, to be discussed hereinafter.

The body I preferably includes a frusto-conical forward section I, which merges into a uniformly cylindrical section 8 that constitutes the remainder of the shell.

The inner body 6 has a conical forward end section 9 which is, as best seen in Figs. 1 and 3, substantially coextensive with the section 1. Together, sections 7 and 9 constitute a diffuser, and define between them a passage IQ of annular cross section that increases in area from the front end of the missile, shown at H, to the inner extremity l2 of the section 9. In the preferred proportions, the area of cross section of the passage at the inner extremity of base l2 of the cone is approximately 25% greater than the area at the front end II.

From the base l2 rearward, the passage It) remains of substantially constant cross section to a point I3, from which the inner body 6 tapers to a point [5, forming a surface of revolution [4 of ogival shape. Thereby, the cross sectional area of the passage H3 is again increased. Finally said passage merges into a combustion chamber 16 and terminates as the tail pipe outlet H at the rear end of the missile.

The inner body 6 is, of course, supported and positioned within the body I by conventional As best seen in Fig. 2, at front end of the passage [0, the body i may have a thickened portion l9 that shapes the entrance of said passage to improve its supersonic fluid flow admission characteristics.

The inner body 6 is divided into a desired number of compartments by transverse partitions I9 I, to provide accommodations for various components of the missile. The forward portion of conical section 9 carries guidance and control apparatus and the rear of said section contains the explosive charge. The guidance and control apparatus includes radio apparatus, hydraulic mechanism, servomotors and the like, as may be requisite.

The remaining compartments are utilized mainly for fuel storage. This is true because of the relatively great fuel needs of a long-range missile. An important feature to be borne in mind is that the fuel must be stored and consumed in such way that the location of the center of gravity of the entire missile remains substantially fixed as the fuel is consumed progressively during the travel of the missile. With this end in view, the fuel is fed simultaneously from both ends of the missile, at equal rates.

Four compartments 20, 2|, 22 and 23 are shown, by way of example, although it will be understood that any other even number may be provided instead. Between compartments 2| and 22 is a space 24 for accommodating a pressurizing device 24a (Fig. 4) for supplying air under pressure to fuel compartments 20 and 23, to discharge fuel therefrom.

This pressurizing device is operated by energy derived from the air flow through passage l0. Two pitot tubes, 25 and 26, Figs. 3 and l, serve this purpose. They are directed into the air stream and apply the dynamic pressure thereof for the two distinct purposes of operating the turbine of a turbine-compressor unit, and supplying air at enhanced pressure to said compressor for further compression by the latter.

The forwardly directed tube 25 creates pressure from the dynamic energy of the airflow impinging thereon in passage l0, and this operates the turbine 27, whose exhaust air is returned to the passage l through pipe 28. The turbine 2'! is preferably direct-connected to the compressor 29. The latter receives its air from the pitot tube 26 which, like 26, provides an initial pressure increase, and compresses this air for delivery through pipes 30 and 3| to fuel compartments 23 and 20 respectively.

Referring to Fig. 3, it will be seen that compartments 23 and 22 are connected by the pipe 32, opening into the forward end of compartment 23 at the bottom thereof, and discharging into compartment 22 at the top of the rear end of the latter. Similarly, compartment 20 is connected to compartment 2| through a pipe 33, leading from the rear bottom of 20 to the forward top of 2|.

Compartments 2| and 22 are connected by a common fuel outlet pipe 3 1 which in turn is connected through a T 35 to the fuel line 36 that leads to the fuel feed-control means 31. From feed-control means 37 the fuel is fed in properly adjusted flow to the burner jets which are arranged uniformly about an injector ring 38 to provide properly distributed combustion. At 39 is indicated a flame holder which initially ignites the fuel and re-lights it if necessary.

At 40 are indicated generally the aft guidance mechanisms which control steering of the missle by turning the vanes 4, 4, 5, 5, already described. These mechanisms 40 are under the control of the guidance apparatus located at the forward end of conical section 9.

The operation of the missile will be evident from the structural features, but may be summarized briefly as follows:

A suitable launching device is used to bring the missile to operating speed in the air, for example, a booster rocket or assemblage of such rockets. These are so connected to the missile that they drop off automatically when spent, so that the missile need not carry them along.

When the necessary speed has been attained, the flow of air through passage I0 at a supersonic rate will suffice to sustain ram-jet action. The burners will thereupon maintain the missile in flight. Fuel will be fed simultaneously from both end compartments, 20 and 23, due to the pressurizing action of the air compressor 29. After these compartments are emptied, the fuel supply will continue from compartments 2| and 22.

Due to this feeding from both ends of the missile, its center of gravity remains substantially fixed, which assists materially in maintaining the missile in stable flight.

The guidance apparatus in the forward end of section 9 and the mechanisms 40 may include radio controlled means for determining the course of the missile, and any necessary electrical and/or mechanical devices for controlling the steering vanes.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A ramjet vehicle comprising a substantially tubular outer body having a tapered nose portion defining a forward ram opening, a cylindrical inner body secured coaxially within said outer body, a pointed nose section on said inner body extending within the tapered nose portion of said outer body, said inner and outer body defining an annular ram channel therebetween, said ram channel increasing in cross sectional area from the ram opening to the base of the nose section to reduce the velocity and increase the pressure of a fluid flow in the ram channel, a portion of said ram channel intermediate the ends of said inner and outer bodies having a substantially constant cross sectional area, said inner body terminating short of the rear end of said outer body and cooperating with said outer body to define a combustion chamber in said vehicle, wings secured to said outer body adjacent the center of gravity of said vehicle, control surfaces connected to said outer body adjacent the rear end thereof, operating means for said control surfaces, control means located in the nose of said inner body for energizing said operating means, a plurality of fuel tanks in said inner body arranged symmetrically about the center of gravity of said vehicle, a plurality of compartments in each of said tanks, a common fuel conduit for discharging fuel concurrently from each of said tanks to said combustion chamber, pressurizing means supplying pressure to each of the several tank compartments most remote from the common fuel conduit, and connections between the sequential compartments of a tank, said connections including a pipe extending from the bottom of the more remote compartment to the top of the next compartment in sequence whereby the compartments are emptied in the order of the greatest remoteness from the common fuel conduit.

2. A ramjet vehicle comprising a body having a ram opening, an inner body secured within said outer body, said inner and outer body defining an annular ram channel therebetween, a combustion chamber in said vehicle, a burner in said combustion chamber, a plurality of fuel tanks in said inner body, a plurality of compartments in each of said tanks, a common fuel outlet ccnnecting said tanks to said burner, said tanks being spaced apart to define a chamber in said inner body, a fluid motor in said chamber, connections for supplying driving fluid to said motor from said ram channel, a fluid compressor driven by said motor, connections for supplying fluid from said ram channel to said compressor, connections supplying pressure from said compressor to the several tank compartments most remote from the common fuel outlet, and connections between the sequential compartments of each tank including means defining a passage extending from the bottom of the more remote to the top of the next compartment in sequence.

3. A ramjet vehicle comprising an outer body having a forward ram opening, an inner body within said outer body, said inner and outer body defining a ram channel therebetween, said inner body terminating short of the rear end of said outer body, a combustion chamber in said vehicle, wing members secured to said outer body adjacent the center of gravity of said vehicle, control surfaces connected to said outer body adjacent the rear end thereof, a plurality of fuel tanks in said inner body arranged symmetrically about the center of gravity of said vehicle, a plurality of compartments in each of said tanks, a common fuel outlet for concurrently delivering fuel from said tanks to the combustion chamber, a compressor supplying pressure to the several tank compartments most remote from the common fuel outlet, and connections between sequential compartments of each tank, said connections including a pipe extending from the bottom of the more remote compartment to the top of the next compartment in sequence whereby the compartments are emptied in the order of the greatest remoteness from the center of gravity of the vehicle.

4. A ramjet vehicle comprising an outer body, an inner body within said outer body, said inner and outer body defining a ram channel therebetween, a combustion chamber in said vehicle, a plurality of fuel tanks in said inner body arranged symmetrically with respect to the center of gravity of said vehicle, a plurality of compartments in each of said tanks, a common fuel outlet for concurrently discharging fuel from each of said tanks into said combustion chamber, there being a chamber in said inner body, a fluid motor in said chamber, a tube extending from said motor into said ram channel for supplying driving fluid to said motor, a fluid compressor driven by said motor, connections supplying fluid from said ram channel to said compressor, connections supplying fluid under pressure from said compressor to the several tank compartments most remote from the common fuel outlet and connections between sequential compartments of each tank, said connections including a pipe ex- 6 tending from the bottom of the more remote compartment to the top of the next compartment in sequence, whereby the compartments are emptied in the order of the greatest remoteness from the center of gravity of the vehicle.

5. A ramjet vehicle comprising an outer body, an inner body secured within said outer body, said inner and outer bodies defining an annular ram channel therebetween, a combustion chamber in said vehicle, a burner in said combustion chamber, a plurality of fuel tanks in said inner body arranged symmetrically with respect to the center of gravity of the vehicle, a plurality of compartments in each of said tanks, a commcn fuel conduit simultaneously connecting said tanks to said burner, a compressor deriving energy from a fluid flow in said ram channel, connections delivering fluid under pressure from said compressor to the tank compartments most remote from the common conduit, and means defining a passage between the bottom of each compartment and the top of the succeeding compartment.

6. A ramjet vehicle comprising an outer body having a forward ram opening, an inner body secured within said outer body, said inner and outer body defining a ram channel therebetween, a combustion chamber in said vehicle, a plurality of fuel tanks in said inner body, said tanks being located symmetrically with respect to the center of gravity of said vehicle, a plurality of compartments in each of said tanks, a common fuel conduit concurrently conveying fuel from each of said tanks to said combustion chamber, pressurizing means supplying fluid under pressure to each of said tanks, the pressure being supplied to the tank compartments most remote from the common fuel outlet, and connections between the sequential compartments of each individual tank, said connections including a pipe extending from the bottom of the more remote compartment to the top of the next compartment in sequence whereby the compartments are emptied in the order of the greatest remoteness from the center of gravity of said vehicle.

References {lited in the file of this patent UNITED STATES PATENTS Number Name Date 980,243 Gillmor Jan. 3, 1911 1,296,333 Shonnard Mar. 4, 1919 2,206,809 Denoix July 2, 1940 2,410,538 Walton Nov. 5, 1946 2,413,621 Hammond, Jr Dec. 31, 1946 2,419,866 Wilson Apr. 29, 1947 2,457,393 Muffiy Dec. 28, 1948 2,482,505 Pierce Sept. 20, 1949 2,540,594 Price Feb. 6, 1951 FOREIGN PATENTS Number Country Date 625,104 France Apr. 19, 1927 516,818 Great Britain Jan. 12, 1940 866,598 France May 26, 1941 

